Laser clad fuel injector premix barrel

Patent metadata

Field	Value
Publication number	US-9989259-B2
Application number	US-201514879182-A
Country	US
Kind code	B2
Filing date	Oct 9, 2015
Priority date	Mar 1, 2012
Publication date	Jun 5, 2018
Grant date	Jun 5, 2018

Abstract

A fuel injector for a gas turbine engine may include a center body disposed about a longitudinal axis, and a premix barrel positioned radially outwardly from the center body to define an annular passageway between the center body and the premix barrel. The annular passageway may extend from an upstream end that is configured to be fluidly coupled to a compressor to a downstream end that is configured to be fluidly coupled to a combustor. The premix barrel may include a first portion at the upstream end and a second portion at the downstream end. The first portion may include a stainless steel material, and the second portion may include a nickel based superalloy material. The second portion may be coupled to the first portion by a laser clad coupling.

First claim

What is claimed is:

1. A method of fabricating a premix barrel of a gas turbine fuel injector, the premix barrel having an outlet at a downstream end, the method comprising:
machining an annular groove on a tubular component extending along a longitudinal axis;
depositing a cladding on the groove using laser cladding; and
machining the cladded tubular component to form the premix barrel, wherein the premix barrel includes the cladding extending as a hollow tube along the longitudinal axis from one end of the tubular component to the outlet of the premix barrel.

2. The method of claim 1 , wherein:
machining the annular groove includes creating a region of reduced thickness of the tubular component along a length of the tubular component, and
machining the cladded tubular component includes removing the region of reduced thickness of the tubular component to expose a bottom surface of the cladding.

3. The method of claim 1 , wherein machining the annular groove includes machining the groove to have a base and an inclined side wall.

4. The method of claim 3 , wherein machining the cladded tubular component includes removing the base of the groove such that the cladding is connected to the tubular component only at the inclined side wall.

5. The method of claim 3 , wherein depositing the cladding includes depositing a thickness of the cladding that is greater than a thickness of the base.

6. The method of claim 1 , wherein machining the cladded tubular component includes forming the premix barrel having an outer diameter of the cladding greater than an outer diameter of the tubular component.

7. The method of claim 6 , wherein machining the cladded tubular component further includes forming the premix barrel having an inner diameter of the cladding equal to an inner diameter of the tubular component.

8. The method of claim 1 , wherein machining the cladded tubular component includes creating the cladding having a length between about 0.5-2.5 inches and a thickness between about 0.15-0.5 inches.

9. A method of fabricating a premix barrel of a gas turbine fuel injector, the premix barrel having an outlet at a downstream end, the method comprising:
creating an annular groove along a length of a tubular component;
depositing a cladding on the groove using laser cladding; and
machining the cladded tubular component to form the premix barrel, wherein the machining includes removing at least a portion of the tubular component below the deposited cladding to expose a bottom surface of the cladding, the cladding extending to the outlet of the premix barrel.

10. The method of claim 9 , wherein creating the annular groove includes machining the groove to have a base and a side wall, and machining the cladded tubular component includes removing the base of the groove such that the cladding is connected to the tubular component only at the side wall.

11. The method of claim 9 , wherein removing at least the portion of the tubular component below the deposited cladding includes forming the cladding that extends as a hollow tube from one side of the tubular component.

12. The method of claim 9 , wherein depositing the cladding includes depositing a thickness of the cladding that is greater than a thickness of the tubular component below the deposited cladding.

13. The method of claim 12 , wherein machining the cladded tubular component includes forming the premix barrel having an outer diameter of the cladding greater than an outer diameter of the tubular component.

14. The method of claim 13 , wherein machining the cladded tubular component further includes forming the premix barrel having an inner diameter of the cladding equal to an inner diameter of the tubular component.

15. The method of claim 9 , wherein machining the cladded tubular component includes machining such that a portion of the cladding having an exposed bottom surface has a length between about 0.5-2.5 inches and a thickness between about 0.15-0.5 inches.

Assignees

• Solar Turbines Inc

Inventors

• Krichever Alexander Ilich
• Corr Ii Robert Anthony
• Barker Peter
• Montague John Preston

Classifications

• B23K26/34

  Laser welding for purposes other than joining · CPC title

• B23K2103/08

  Non-ferrous metals or alloys · CPC title

• B23K26/342

  Build-up welding · CPC title

• Y10T29/49323

  Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles · CPC title

• B23K26/0006

  taking account of the properties of the material involved (B23K26/32, B23K26/40 take precedence) · CPC title